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11.发明申请TURBINE AIRFOIL TIP SHELF AND SQUEALER POCKET COOLING 有权TURBINE AIRFOIL TIP SHELF和SQUEALER POCKET COOLING公开(公告)号：US20150118063A1
公开(公告)日：2015-04-30
申请号：US14250166
申请日：2014-04-10
Applicant: United Technologies Corporation
CPC classification number: F01D5/20 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: An airfoil comprises pressure and suction surfaces extending from a root section to a tip section of the airfoil. The airfoil also comprises a leading edge and trailing edge defining a chord length therebetween. A tip shelf is formed along the tip section between the pressure surface and a tip shelf wall, the tip shelf wall being spaced between the pressure surface and the suction surface. A squealer pocket is formed along the tip section between the tip shelf wall and a squealer tip wall extending from the suction surface. The tip shelf extends from within 10% of the cord length measured from the leading edge to within 10% of the chord length measured from the trailing edge. The squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate less than 85% of the chord length measured from the trailing edge.
Abstract translation: 翼型件包括从根部延伸到翼型的尖端部分的压力和吸力表面。 翼型件还包括在其间限定弦长的前缘和后缘。 沿着压力表面和尖端搁板壁之间的尖端部分形成尖端搁板，顶部搁板壁在压力表面和吸力表面之间分开。 沿尖端搁架壁和从抽吸面延伸的尖叫尖端壁之间的尖端部分形成一个尖叫口袋。 尖端架从从前缘测量的绳索长度的10％范围内延伸到从后缘测量的弦长的10％以内。 尖叫口袋从前缘测量的弦长的10％范围内延伸，以终止从后缘测得的弦长不到85％。
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公开(公告)号：US10773344B2
公开(公告)日：2020-09-15
申请号：US15625688
申请日：2017-06-16
Inventor： Scott D. Lewis , Stephen Lynch , Shane Haydt
IPC: B23K26/00 , B23K26/384 , F01D5/18 , B23H9/14 , B23H1/04 , F23R3/00 , F01D9/06 , B23H9/10 , F23R3/06 , B23H7/24 , F01D9/02 , F01D25/12 , F02K1/82
Abstract: An electrode for electrical discharge machining (EDM) may comprise a diffuser portion and a tapered portion defining the tip of the electrode.A method for forming a film cooling hole may comprise moving a tool with respect to a film cooled gaspath component, forming a diffuser of the film cooling hole in response to the moving, and forming a tapered surface between a metering section and the diffuser of the film cooling hole.
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公开(公告)号：US10533428B2
公开(公告)日：2020-01-14
申请号：US15613923
申请日：2017-06-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Scott D. Lewis
Abstract: A turbine blade may comprise a pressure side wall and a suction side wall opposite the pressure side wall. A tip wall may extend between the pressure side wall and the suction side wall and may comprise a first opening. A first dimension of the first opening may be greater than a second dimension of the first opening. The first dimension may be oriented in a direction extending from a leading edge of the turbine blade toward a trailing edge of the turbine blade.
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公开(公告)号：US20190383153A1
公开(公告)日：2019-12-19
申请号：US16521854
申请日：2019-07-25
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis , Dominic J. Mongillo, JR. , Mark F. Zelesky , Bret M. Teller , Russell Deibel , Matthew S. Gleiner
Abstract: A vane according to an exemplary aspect of the present disclosure includes, among other things, a platform extending from an edge face and between spaced apart lateral faces and an airfoil extending outwardly from the platform. The platform includes at least one ejection port in the edge face and at least one passage connected to the at least one ejection port. A method of cooling a component is also disclosed.
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公开(公告)号：US10208603B2
公开(公告)日：2019-02-19
申请号：US14942025
申请日：2015-11-16
Applicant: United Technologies Corporation
Inventor： JinQuan Xu , Scott D. Lewis
Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a first reference plane extending in a spanwise direction and through a thickness of the internal wall. A first cavity and a second cavity are separated by the internal wall. A plurality of crossover passages within the internal wall connects the first cavity to the second cavity. The plurality of crossover passages are arranged such that the passage axis of each of the plurality of cooling passages intersects a surface of the second cavity.
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Patent Agency Ranking
公开(公告)号：US10145246B2
公开(公告)日：2018-12-04
申请号：US14820786
申请日：2015-08-07
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis , Yafet Girma , Christopher Corcoran
Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a first reference plane extending in a spanwise direction and through a thickness of the internal wall. A first cavity and a second cavity are separated by the internal wall. A plurality of crossover passages within the internal wall connects the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The plurality of crossover passages are distributed in the spanwise direction and arranged such that the passage axis of each of the plurality of cooling passages intersects a surface of the second cavity. The plurality of crossover passages include a first set of crossover passages and a second set of crossover passages positioned on opposite sides of the first reference plane. The passage axis of each of the first set of crossover passages is arranged at a first vertical angle relative to a spanwise axis, and the passage axis of each of the second set of crossover passages is arranged at a second, different vertical angle relative to the spanwise axis. A casting core for an airfoil is also disclosed.
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公开(公告)号：US20180073369A1
公开(公告)日：2018-03-15
申请号：US15266855
申请日：2016-09-15
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis , Dominic J. Mongillo , Atul Kohli
CPC classification number: F01D5/186 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/12 , F04D29/083 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/303 , F05D2250/38 , F05D2260/201 , F05D2260/202 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges to provide an exterior airfoil surface. The pressure and suction side walls are spaced apart from one another in a thickness direction. A stagnation line is located near the leading edge. A cooling passage is provided between the pressure and suction side walls. The showerhead cooling holes are arranged at least one of adjacent to or on the stagnation line. At least one of the showerhead cooling holes has a metering hole fluidly connecting the cooling passage to a diffuser arranged at the exterior airfoil surface. At least one showerhead cooling hole is arranged on each of opposing sides of the stagnation line. Each showerhead cooling hole has the diffuser with a first diffuser angle that expands downstream in the thickness direction in opposing directions from one another when separated by the stagnation line.
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公开(公告)号：US20170362951A1
公开(公告)日：2017-12-21
申请号：US15676152
申请日：2017-08-14
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis
CPC classification number: F01D11/08 , F01D5/081 , F01D5/10 , F01D5/3007 , F01D11/008 , F01D25/06 , F01D25/12 , F05D2220/32 , F05D2230/60 , F05D2240/12 , F05D2240/307 , F05D2240/55 , F16J15/162 , Y02T50/672 , Y02T50/675
Abstract: A seal arrangement for a gas turbine engine according to an example of the present disclosure includes, among other things, a component including a body having a cold side surface adjacent to a mate face, and a seal member including a leading edge region and a trailing edge region spaced by sidewalls. The seal member defines one or more grooves. A length of the one or more grooves abuts the cold side surface to define one or more cooling passages, with at least one of the one or more cooling passages having a flared inlet defined by a corresponding one of the one or more grooves.
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公开(公告)号：US09822658B2
公开(公告)日：2017-11-21
申请号：US14945835
申请日：2015-11-19
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis
CPC classification number: F01D11/08 , F01D5/081 , F01D5/10 , F01D5/3007 , F01D11/008 , F01D25/06 , F01D25/12 , F05D2220/32 , F05D2230/60 , F05D2240/12 , F05D2240/307 , F05D2240/55 , F16J15/162 , Y02T50/672 , Y02T50/675
Abstract: A seal arrangement for a gas turbine engine according to an example of the present disclosure includes, among other things, a component including a body having a cold side surface adjacent to a mate face, and a seal member including a leading edge region and a trailing edge region spaced by sidewalls. The seal member defines one or more grooves. The one or more grooves abut the cold side surface to define one or more cooling passages, with at least one of the one or more cooling passages having a flared inlet defined by a corresponding one of the one or more grooves.
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公开(公告)号：US20170101870A1
公开(公告)日：2017-04-13
申请号：US14880900
申请日：2015-10-12
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis , Karen A. Thole , Robert Schroeder
IPC: F01D5/18
Abstract: A component of a gas turbine engine is provided including at least one cooling hole formed in the component. The cooling hole has an interior surface that defines a flow path for air configured to cool a portion of the component. A feature is arranged within at least a portion of the cooling hole. The feature is configured to generate non-linear movement of the air as it flows there through.
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